SA7035 (sa7035-il)
SA7035 - Selig / Ashok Gopalarathnam SA7035
| Details | Dat file | Parser | |
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(sa7035-il) SA7035 Selig / Ashok Gopalarathnam SA7035 Max thickness 9.2% at 27.9% chord. Max camber 2.4% at 41.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
SA7035
1.00000 .00000
.99815 .00017
.99265 .00079
.98367 .00197
.97138 .00375
.95600 .00615
.93777 .00913
.91689 .01264
.89359 .01657
.86806 .02082
.84049 .02528
.81106 .02984
.77993 .03442
.74727 .03894
.71326 .04334
.67810 .04760
.64203 .05168
.60526 .05549
.56801 .05899
.53053 .06214
.49301 .06485
.45566 .06712
.41872 .06887
.38237 .07007
.34681 .07071
.31224 .07073
.27881 .07012
.24673 .06888
.21613 .06699
.18713 .06448
.15991 .06134
.13456 .05759
.11118 .05331
.08989 .04850
.07072 .04323
.05378 .03760
.03911 .03165
.02670 .02552
.01662 .01937
.00895 .01331
.00365 .00752
.00075 .00224
.00048 -.00179
.00371 -.00497
.01052 -.00821
.02026 -.01131
.03286 -.01407
.04832 -.01642
.06658 -.01840
.08751 -.02002
.11103 -.02126
.13700 -.02212
.16529 -.02262
.19574 -.02278
.22816 -.02262
.26238 -.02216
.29819 -.02144
.33536 -.02048
.37368 -.01932
.41289 -.01800
.45274 -.01655
.49296 -.01498
.53331 -.01329
.57358 -.01151
.61352 -.00973
.65286 -.00799
.69133 -.00635
.72863 -.00485
.76451 -.00351
.79869 -.00236
.83091 -.00140
.86091 -.00064
.88847 -.00005
.91340 .00039
.93553 .00069
.95469 .00082
.97069 .00079
.98337 .00062
.99256 .00037
.99813 .00012
1.00000 .00000
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Polars for SA7035 (sa7035-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sa7035-il | 50,000 | 9 | 33.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 50,000 | 5 | 37.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7035-il | 100,000 | 9 | 52.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 100,000 | 5 | 53.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7035-il | 200,000 | 9 | 71.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 200,000 | 5 | 68 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7035-il | 500,000 | 9 | 94.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 500,000 | 5 | 87.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7035-il | 1,000,000 | 9 | 111.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 1,000,000 | 5 | 101.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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